2)  Check that cable tension is within values shown in Fig. 507. Repeat steps (b) thru (g).
NOTE:  After adjustment, rigging pin SB-2 need not fit in rigging pin hole.
3)  Install turnbuckle locking clips.
(j)  Install two grease fitting access covers.
(9)  Test Spoiler Control System per par. 3.
D.  Restore Airplane to Normal
(1)  
Remove system A and B hydraulic power (Ref 27-61-0 MP).

(2)  
Remove protractor and protractor mount from captain's control wheel.

(3)  
Remove electrical power if no longer required.

3.  Spoiler Control System Test
A.  General
(1)  This test checks operation of flight spoilers (No. 2, 3, 6, and 7). Refer to 27-62-0, Speed Brake Control System - Adjustment/Test, for test of ground spoilers (No. 1, 4, 5, and 8), and speed brake operation of flight spoilers.
B.  Equipment and Materials
(1)  
Control Surface Protractor - 4MIT65B80307-1 (preferred), F52485-500 (optional) (3 required)

NOTE:  Two protractors with stands (item (2)) are for measuring angular position of spoiler panels. Protractor may be hand-held on spoiler instead of using stand. One protractor with mount (item (3)) is for measuring angular position of control wheel.

(2)  
Control Surface Protractor Stand Assembly - F71292-17 (optional) (2 required)

(3)  
Aileron Control Wheel Protractor Mount - F72790

(4)  
Rigging Pins Kit - F70207-3, -52, -61, or -84:

REF NO.  F70207-( )  DIAMETER (INCHES)  LENGTH (INCHES)  FUNCTION 
A/S-14  -8  0.309-0.311  6.7 ± 0.25  Aileron bus drum 

500 
Feb 20/88  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  27-61-0 Page 519 

C.  Prepare for Test
(1)  
Install protractor mount and protractor on captain's control wheel. With control wheel in zero position, set protractor to zero.

(2)  
Install control surface protractor stand and protractor on flight spoiler No. 7. Set protractor to zero.

NOTE: Protractor may be hand-held on spoiler instead of using stand.

(3)  
Provide system A and B hydraulic power (Ref 27-61-0 MP).

D.  Test Spoiler Control System
(1)  
Test Spoiler Response at Zero Speed Brake

(a)  
Set aileron in neutral. Aileron is in neutral when rigging pin A/S-4 can be freely inserted. Remove rigging pin.

(b)  
Place speed brake control lever in DOWN position.

(c)  
Rotate captain's aileron control wheel clockwise. Check that spoiler No. 7 begins to rise at 9 ± 1 degrees clockwise from zero.

(d)  
Rotate captain's aileron control wheel to 87 degrees clockwise. Check that spoiler No. 7 is 38 ± 2 degrees up from zero position.

(e)  
From wheel position in previous step, return control wheel counterclockwise and check that spoiler No. 7 starts down when wheel is positioned at 70 degrees minimum clockwise from zero.

(f)  
From wheel position in previous step, rotate control wheel counterclockwise and check that all spoilers are full down when wheel is 4 ± 2 degrees clockwise from zero.

(g)  
Install control surface protractor stand and protractor on flight spoiler No. 2. Set protractor to zero.

NOTE: Protractor may be hand-held on spoiler instead of using stand.

(h)  
Rotate control wheel counterclockwise and check that spoiler No. 2 begins to rise at 9 ± 1 degrees counterclockwise from zero.

(i)  
Rotate control wheel to 87 degrees counterclockwise. Check that spoiler No. 2 is 38 ± 2 degrees up from zero position.

(j)  
From wheel position in previous step, return control wheel clockwise and check that spoiler No. 2 starts down when wheel is 70 degrees minimum counterclockwise from zero.

(k)  
From wheel position in previous step, rotate control wheel clockwise and check that all spoilers are full down when the wheel is 4 ± 2 degrees counterclockwise from zero.

(2)  
Test Spoiler Equalization at Partial Speed Brake

(a)  Set speed brake control lever so that spoiler No. 2 is 15 ± 1 degree up from zero position. Check that spoilers No. 3, 6, and 7 are within ± 0.5 degree of spoiler No. 2.

(3)  
Test Spoiler Response at Flight Detent Position of Speed Brake

(a)  Set speed brake control lever in FLIGHT DETENT position and check that: 1) Spoiler No. 2 is 26 ± 2 degrees up from zero position. Record value. 2) Spoiler No. 7 is within ± 1 degree of spoiler No. 2.

(4)  
　
中國航空網(wǎng) www.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：737 AMM 飛機(jī)維護(hù)手冊 飛行操縱 FLIGHT CONTROLS 3(94)